FIELD: rocketry, in particular, all-round defence without discharge of passive mass onto the launching pad. SUBSTANCE: actuating system uses take-off means, aerodynamic control surfaces with a drive, and orientation means based at least on one gas generator and propelling nozzles connected to it. Orientation means are positioned in annular casing intended for braced coupling to tail part of missile body. Inner surface of annular case is cone-shaped and coated with heat-insulating material forming gas passage- nozzle, whose streamline section is continuation of nozzle section of missile sustainer. EFFECT: improved design. 11 cl, 8 dwg
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